Research On Guidance And Control Key Technology Of High Dynamic Intermediate-range Spinning Projectiles

Based on the demand of the high dynamic intermediate-range spinning guidance projectiles,the paper is devoted to the guidance and control key technology for the support of spinning guidance projectiles.The development history and research status of the intermediate-range spinning guidance rocket projectiles is overviewed and the research result and development tendency of key theory and technology such as spinning projectiles stability theory?novel decoupling method?autopilot design method and advanced guidance law is summarized in the paper.Reference frame system and mathematical model of the spinning projectiles is built and simplified to the linear pitch and yaw integrated form.Proportional electric actuator dynamic model is built.Spinning projectiles effect mainly includes inertia coupling?aerodynamic coupling and control coupling.Transfer function of spinning projectiles is derived using complex number analysis method.Influence of inertia coupling and aerodynamic coupling in uncontrolled and controlled condition is simulated?compared and analyzed.Control coupling model is built and influence of actuator dynamic is studied.Feedforward decoupling and output feedback decoupling method is designed for inertia coupling and aerodynamic coupling and diagonal dominance decoupling method is designed for control coupling to support the spinning projectiles decoupling theory.Influence of damping loop ? stabilizing loop and acceleration loop to spinning projectiles is researched and stable boundary formula is derived.Proposing the method based on open loop crossover frequency constraint for two-loop autopilot and three-loop autopilot design and comparing them from the standpoint of response speed?robustness and coupling reduction.A method base on state observer of spinning projectiles decoupling autopilot is proposed and response speed?robustness and coupling reduction ability is verified.It provides a theoretical basis for the guidance projectiles control loop cost degradation.The mathematic model is built according to the two-dimensional relationship between the missile and the target,impact angle is redefined and expect LOS angle and its derivative formula is derived.Based on nonsingular terminal sliding mode control theory?dynamic surface control theory and extended state observer,a novel sliding mode guidance law(FESO-NFTSMGL)is designed with second order autopilot dynamic lag consideration and impact angle constraint,and its stability is proved.Several excellent characters are verified by comparing with the classical terminal sliding mode guidance law and trajectory shaping guidance law,such as reaching quickly?convergence in finite time and high accuracy,and the strong robustness is reflected via simulation of different initial condition.